A polishing method is described for polishing a machine component comprising at least one airfoil portion comprised of a suction side, a pressure side, a leading edge and a trailing edge. The method provides for arranging the machine component in a container and constraining the machine component to the container. A polishing mixture is added in the container, and the container is caused to vibrate together with the machine component constrained thereto, thereby generating a polishing mixture flow along the airfoil portion until a final arithmetic average roughness is achieved.

A turbine and a turbine-generator device for use in electricity generation. The turbine has a universal design and so may be relatively easily modified for use in connection with generators having a rated power output in the range of 50 KW to 5 MW. Such modifications are achieved, in part, through use of a modular turbine cartridge built up of discrete rotor and stator plates sized for the desired application with turbine brush seals chosen to accommodate radial rotor movements from the supported generator. The cartridge may be installed and removed from the turbine relatively easily for maintenance or rebuilding. The rotor housing is designed to be relatively easily machined to dimensions that meet desired operating parameters.

The invention relates to an anti-icing turbomachine blade (26), in particular for a low-pressure compressor or an intermediate-pressure compressor of a turbomachine. The blade (26) has a leading edge (28) formed by an ice-phobic surface (40) and two hydrophobic surfaces (42; 44) which extend the ice-phobic surface (40) on the pressure side (32) and the suction side (34) to allow water droplets escaping from the leading edge (28) to flow.

A tool for a slot in a gas turbine engine, according to an example of the present disclosure, includes a head configured to be received in the slot, a first pad removably bonded to the head with an adhesive, and a second pad removably bonded to the head with an adhesive and disposed opposite from the first pad.

The invention concerns a transition duct for a multi-stage compressor of a gas turbine engine. Regions of the inner surface of the duct are provided with a predetermined and dissimilar surface roughness to optimise gas flow efficiency within the duct.

An impeller manufacturing method includes: integrally forming an impeller by an additive manufacturing method using a metal powder, the impeller including a disk which has a disk shape about an axis, a plurality of blades which are formed on a surface facing a first side in an axial direction of the disk with gaps therebetween in a circumferential direction about the axis, and a cover which covers the plurality of blades from the first side in the axial direction; processing the integrally formed impeller by a hot isostatic pressing; and causing a polishing fluid containing abrasive grains to flow through a flow path formed between the disk, the cover, and the blades in the impeller after the processing with the hot isostatic pressing and while pressurizing the polishing fluid to perform fluid polishing.

A method for smoothing surface roughness within an internal passageway is disclosed. In various embodiments, the method comprises developing a first sphere progression through a length of the internal passageway, each sphere within the first sphere progression having a first sphere diameter greater than or equal to a diameter of the internal passageway; and developing a second sphere progression through the length of the internal passageway, each sphere within the second sphere progression having a second sphere diameter greater than the first sphere diameter, whereby the inner surface of the internal passageway is smoothed, first by the first sphere progression and then by the second sphere progression.

The present invention relates to a method for producing a blade or blade arrangement of a turbomachine, which features the following steps: producing a blade (4) from at least one blade material, machining the blade in at least one region of the blade by a surface machining process, cleaning the surface of the blade depositing an erosion protection coating (10) of at least two layers of different hardness by physical vapor deposition in the at least one region, machining the erosion protection coating (10) by a coating smoothing process in order to establish a defined surface roughness. Furthermore, the invention relates to correspondingly produced blades or blade arrangements.

A method of electropolishing an internal passageway of a component, wherein the passageway has an inlet and an outlet; including: providing an electrode assembly including a flexible electrode, a shuttle and a guide cable extending between the flexible electrode and the shuttle; inserting the shuttle into the inlet; causing fluid to flow through the passageway to transport the shuttle through the passageway from the inlet towards the outlet; pulling the guide cable through the passageway to position the electrode in the passageway adjacent to a region of the passageway to be polished; and electropolishing the passageway using the electrode while moving the electrode within the passageway. Also, an electrode assembly for electropolishing an internal passageway of a component, including: a flexible electrode, a shuttle, and a guide cable extending between the flexible electrode and the shuttle.

A method of manufacturing a component from a nickel-based superalloy comprises the steps of: providing a vacuum induction casting furnace; positioning a component mould onto a chill plate within the furnace; casting a component blank; peening the surface of the component blank; applying a surface modification technique to the surface of the component blank; solution heat treating the component blank at or above the -solvus temperature for the superalloy; and precipitation heat treating the component blank.